Classifications

• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F28—HEAT EXCHANGE IN GENERAL
  • F28F—DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
  • F28F3/00—Plate-like or laminated elements; Assemblies of plate-like or laminated elements
  • F28F3/02—Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations
  • F28F3/04—Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations the means being integral with the element
  • F28F3/042—Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations the means being integral with the element in the form of local deformations of the element
  • F28F3/046—Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations the means being integral with the element in the form of local deformations of the element the deformations being linear, e.g. corrugations
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
  • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
  • F02C7/12—Cooling of plants
  • F02C7/14—Cooling of plants of fluids in the plant, e.g. lubricant or fuel
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
  • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
  • F02C7/24—Heat or noise insulation
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
  • F01N—GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR MACHINES OR ENGINES IN GENERAL; GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR INTERNAL COMBUSTION ENGINES
  • F01N1/00—Silencing apparatus characterised by method of silencing
  • F01N1/02—Silencing apparatus characterised by method of silencing by using resonance
  • F01N1/023—Helmholtz resonators
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
  • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
  • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
  • F02C7/045—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for noise suppression
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
  • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
  • F02C7/12—Cooling of plants
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F28—HEAT EXCHANGE IN GENERAL
  • F28D—HEAT-EXCHANGE APPARATUS, NOT PROVIDED FOR IN ANOTHER SUBCLASS, IN WHICH THE HEAT-EXCHANGE MEDIA DO NOT COME INTO DIRECT CONTACT
  • F28D1/00—Heat-exchange apparatus having stationary conduit assemblies for one heat-exchange medium only, the media being in contact with different sides of the conduit wall, in which the other heat-exchange medium is a large body of fluid, e.g. domestic or motor car radiators
  • F28D1/02—Heat-exchange apparatus having stationary conduit assemblies for one heat-exchange medium only, the media being in contact with different sides of the conduit wall, in which the other heat-exchange medium is a large body of fluid, e.g. domestic or motor car radiators with heat-exchange conduits immersed in the body of fluid
  • F28D1/03—Heat-exchange apparatus having stationary conduit assemblies for one heat-exchange medium only, the media being in contact with different sides of the conduit wall, in which the other heat-exchange medium is a large body of fluid, e.g. domestic or motor car radiators with heat-exchange conduits immersed in the body of fluid with plate-like or laminated conduits
  • F28D1/0391—Heat-exchange apparatus having stationary conduit assemblies for one heat-exchange medium only, the media being in contact with different sides of the conduit wall, in which the other heat-exchange medium is a large body of fluid, e.g. domestic or motor car radiators with heat-exchange conduits immersed in the body of fluid with plate-like or laminated conduits a single plate being bent to form one or more conduits
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F28—HEAT EXCHANGE IN GENERAL
  • F28D—HEAT-EXCHANGE APPARATUS, NOT PROVIDED FOR IN ANOTHER SUBCLASS, IN WHICH THE HEAT-EXCHANGE MEDIA DO NOT COME INTO DIRECT CONTACT
  • F28D9/00—Heat-exchange apparatus having stationary plate-like or laminated conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
  • F28D9/0081—Heat-exchange apparatus having stationary plate-like or laminated conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall the conduits for one heat-exchange medium being formed by a single plate-like element ; the conduits for one heat-exchange medium being integrated in one single plate-like element
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F28—HEAT EXCHANGE IN GENERAL
  • F28F—DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
  • F28F3/00—Plate-like or laminated elements; Assemblies of plate-like or laminated elements
  • F28F3/02—Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F28—HEAT EXCHANGE IN GENERAL
  • F28F—DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
  • F28F3/00—Plate-like or laminated elements; Assemblies of plate-like or laminated elements
  • F28F3/02—Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations
  • F28F3/025—Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations the means being corrugated, plate-like elements
  • F28F3/027—Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations the means being corrugated, plate-like elements with openings, e.g. louvered corrugated fins; Assemblies of corrugated strips
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F28—HEAT EXCHANGE IN GENERAL
  • F28D—HEAT-EXCHANGE APPARATUS, NOT PROVIDED FOR IN ANOTHER SUBCLASS, IN WHICH THE HEAT-EXCHANGE MEDIA DO NOT COME INTO DIRECT CONTACT
  • F28D21/00—Heat-exchange apparatus not covered by any of the groups F28D1/00 - F28D20/00
  • F28D2021/0019—Other heat exchangers for particular applications; Heat exchange systems not otherwise provided for
  • F28D2021/0021—Other heat exchangers for particular applications; Heat exchange systems not otherwise provided for for aircrafts or cosmonautics
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F28—HEAT EXCHANGE IN GENERAL
  • F28D—HEAT-EXCHANGE APPARATUS, NOT PROVIDED FOR IN ANOTHER SUBCLASS, IN WHICH THE HEAT-EXCHANGE MEDIA DO NOT COME INTO DIRECT CONTACT
  • F28D21/00—Heat-exchange apparatus not covered by any of the groups F28D1/00 - F28D20/00
  • F28D2021/0019—Other heat exchangers for particular applications; Heat exchange systems not otherwise provided for
  • F28D2021/0049—Other heat exchangers for particular applications; Heat exchange systems not otherwise provided for for lubricants, e.g. oil coolers
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F28—HEAT EXCHANGE IN GENERAL
  • F28F—DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
  • F28F2265/00—Safety or protection arrangements; Arrangements for preventing malfunction
  • F28F2265/28—Safety or protection arrangements; Arrangements for preventing malfunction for preventing noise
• • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
  • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
  • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
  • Y02T50/00—Aeronautics or air transport
  • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

• the present invention relates to a heat exchange panel and noise reduction for a turbomachine, in particular aircraft.
• a turbomachine such as a turbofan engine, conventionally comprises an air inlet comprising a fan whose outlet air flow is divided into a flow of air which enters the engine and forms a hot flow or flow primary, and a flow of air flowing around the engine and forming a cold flow or secondary flow.
• the engine typically comprises, from upstream to downstream, in the direction of flow of the gases, at least one compressor, a combustion chamber, at least one turbine, and an exhaust nozzle in which the combustion gases exit the turbine. and forming the primary stream are mixed with the secondary stream.
• the fan of the turbomachine is surrounded by a fan casing which is integrated with the nacelle of the turbomachine. It is known to line the inner surface of this housing with acoustic panels to limit the propagation of the noise generated by the fan.
• the casing can also be equipped with surface oil heat exchangers type SACOC (acronym for Surface Air Cooled OR Cooler).
• An exchanger of this type comprises an outer surface to be swept by the secondary air flow and on which fins are located, and at least one oil circulation chamber extending under the outer surface. The outer surface is intended to evacuate the heat energy provided by the oil.
• the heat energy of the oil to be dissipated can be very high, the oil can reach up to 160 ° C.
• Some turbomachines have relatively short nacelles in longitudinal dimension. There is therefore less room to install equipment and in particular heat exchangers and acoustic panels to attenuate the noise of the blower.
• the present invention proposes an improvement to this technology, which in particular makes it possible to optimize the design and layout of the air / oil heat exchange and acoustic treatment functions on an installation zone.
• the invention proposes a heat exchange and noise reduction panel for a turbomachine, in particular an aircraft, the panel comprising:
• At least one oil circulation chamber extending between said outer surface and said at least one cavity, and intended to evacuate the heat energy brought by the oil, the stack of said outer surface, said at least one cavity and said at least one chamber extending substantially in the first predetermined direction,
• said channels are at least partly formed in said fins.
• Helmholtz resonator is understood to mean an acoustic system comprising a neck, generally of small size, connected to a cavity of larger size and capable of resonating.
• the neck provides communication between the sound waves to attenuate and the cavity.
• the neck provides visco-thermal dissipation (rapid and alternating movements of sound waves through collars that dissipate sound energy by friction).
• the tuning in frequency that is to say the optimization which makes it possible to generate these maximum speeds at the frequencies to be attenuated, is done mainly via the volume of the resonant cavities, that is to say their dimensions and in particular their height. It should be noted that, given the thermal environment, local temperatures may be taken into account to optimize the system properly.
• the invention thus proposes to combine the aforementioned functions of air / oil heat exchanger and acoustic treatment in the same equipment in the form of a panel. Furthermore, the invention makes it possible, for a given tuning frequency, to reduce the size of the air cavities of the resonators by means of channels of much greater length. From an acoustic point of view, to optimize the operation of the system at a given frequency, the elongation of the collars (channels) of the resonators makes it possible to increase the mass of air in motion and thus to compensate for the small volume of the resonant cavities. In addition, reducing the volume of the resonant cavities has a positive impact on the equipment. Indeed, it would be possible to reduce the overall size of the equipment, or to increase the volume of the oil chamber to thereby reduce the pressure loss generated by the channels in the oil chamber.
• the panel according to the invention may comprise one or more of the following features, taken separately from each other or in combination with each other:
• the fins are substantially normal or inclined with respect to the external surface
• said channels open on walls of the fins to form air intake orifices of said air flow
• each fin is crossed by several channels
• the channels have a section of substantially rectangular, circular or elliptical shape
• the panel has a generally curved shape and is configured to form a sector of an annular envelope of heat exchange and noise reduction, for example for a turbomachine nacelle,
• the channels have a constant section or a general shape flared towards said cavities
• said first direction is substantially perpendicular to said external surface or inclined with respect to said external surface.
• the present invention also relates to a turbomachine, in particular an aircraft, characterized in that it comprises at least one panel as described above.
• FIG. 1 is a very schematic perspective view of a heat exchange and noise reduction panel according to the invention
• FIG. 2 is a view in section and in perspective along line 11-11 of FIG. 1,
• FIG. 3 is a sectional view along the line III-III of FIG. 1,
• FIG. 4 is a sectional view along the line IV-IV of FIG. 1,
• FIG. 5 is a plan view of the panel of FIG. 1,
• FIGS. 6 to 9 are views similar to that of FIG. 4 and illustrating other embodiments of the invention.
• FIG. 1 to 5 shows an embodiment of a panel 10 according to the invention heat exchange and noise reduction for an aircraft turbine engine.
• a “height” refers to a dimension that extends vertically or from the bottom up (or vice versa), a “thickness”, a “length” and a “width”, or even a “distance”, s' mean dimensions measured in a substantially horizontal plane.
• the panel 10 essentially comprises three parts or superposed layers, namely:
• an external part 12 intended to be exposed to a flow of cooling air, such as a secondary air flow of the turbomachine,
• an intermediate portion 14 comprising a chamber 16 for circulating oil to be cooled
• an internal part 18 comprising air cavities 20.
• Parts 12 and 14 form a SACOC type surface heat exchanger and parts 12, 14 and 18 form an acoustic panel with Helmholtz resonators.
• the outer portion 12 comprises an outer surface 22 which is intended to be swept by the air flow 24 and on which are located fins 26.
• the fins 26 extend in a first main direction, here vertical, as well as in a second main direction here horizontal, from the surface 24.
• the first and second directions are substantially perpendicular.
• the horizontal direction perpendicular to the first and second directions is defined as the third direction.
• Air circulates between the fins 26 which are intended in particular to increase the heat exchange surfaces with the air.
• the fins 26 are preferably rectilinear, parallel and independent, that is to say that they are not interconnected.
• the outer surface 22 is shown here with a substantially square or rectangular shape of area or area noted A. Although the surface 22 is here presented as planar it could have a curved shape particularly when the panel 10 is curved to facilitate its mounting in an annular housing of the turbomachine for example.
• a panel 10 of generally curved shape is configured to form a sector of an annular envelope of heat exchange and noise reduction, for example for a turbomachine nacelle.
• the fins 26 extend over substantially the entire length or longitudinal dimension of the surface 22, in the second horizontal direction. Their number is defined in known manner, depending in particular on the exchange conditions to be satisfied.
• the oil circulation chamber 16 extends under the outer surface 22 over substantially its entire extent. It is connected to an inlet and an oil outlet, which are not shown in the drawings.
• the direction and the direction of circulation of the oil in the chamber can be the same as the one (s) of the air on the surface 22 (arrow 28) or little (Fri) t be different (s).
• the air cavities 20 of the third portion 18 are located under the oil chamber 16. They are preferably regularly distributed and substantially identical. They extend alongside each other in the same plane substantially parallel to the surface 22. These cavities 20 are connected to lower longitudinal ends of air passage channels 30 whose upper longitudinal ends form communication orifices 32. with the sound source to attenuate.
• the assembly formed by the channels 30 and the cavities 20 form Helmholtz resonators, the channels forming necks and the cavities forming resonant cavities of the resonators. At least some of the cavities 20 may communicate with one another as shown in FIGS. 7 and 8.
• the invention proposes a panel with a reduced bulk, thanks to the formation of at least a portion of the channels 30 in the fins 26.
• the channels 30 have substantially straight and vertical orientations and comprise lower parts extending in the oil chamber 16 and upper parts extending in the fins 26.
• the channels 30 have their upper ends which open on the walls of the fins, in particular on the tops or upper free end of the fins 26 and form the aforementioned communication orifices 32.
• each fin 26 is traversed by several channels 30.
• the channels 30 are distributed in matrix.
• the channels 30 are distributed in rows and columns in the oil chamber 26.
• each fin 26 comprises a row of orifices 32.
• the panel 10 according to the invention can have the following dimensions, which are optimized to attenuate as much as possible the acoustic frequencies of a turbomachine, namely those between 400 and 2000HZ: the fins 26 have a thickness e (that is to say a dimension along the third direction) of between 0.5 and 2 mm and are spaced from each other by a distance a (in the third direction) between 1 and 5mm,
• the oil chamber 16 has a height ç (in the first vertical direction) of between 1 and 10 mm,
• the channels 30 have an average diameter of between 1 and 2 mm
• the cavities 20 have a height f (in the first vertical direction) of between 5 and 150 mm, and
• the perforation rate ⁇ of said external surface is between 5 and 10%.
• This perforation ratio is equal to the ratio of the cumulative sections of the orifices 32 (n.7t. (D / 2) 2 , n being the number of orifices 32 or channels 30) with the area A of the surface of the resonators, that is considered substantially equal to the outer surface 22.
• the difference between the outer surface and that of the resonators may be negligible.
• the resonators are separated by walls reducing their area relative to the outer surface. But as a first approximation, the two surfaces are equivalent.
• diameter is meant the diameter of a channel when it is cylindrical, the average of the diameters of a channel when it has a non-constant circular section and is, for example, flared or frustoconical, and the diameter of a circular section equivalent to the section of the channel when the latter is not circular and is for example rectangular.
• the tuning frequency of a Helmholtz resonator can be approximated by the following formula: Freq, alright
• the section of the neck S returns to the aforementioned section of an orifice 32
• the volume of the resonator V returns to the volume of a cavity 20
• the fins 26 have a height b (in the first vertical direction) of between 10 and 25 mm, and
• the orifices 32 are, in the same row, are spaced from each other by a distance g (in the second direction) between 1, 57 and 31, 42mm.
• the spacing between the orifices of two adjacent rows returns to the spacing a (in the third direction) between two adjacent fins 26.
• the channels 30 have longitudinal axes substantially perpendicular to said outer surface 22 or inclined relative to said outer surface 22. They have a generally cylindrical longitudinal shape with a constant or parallelepipedal section in the example shown in FIGS. 1 to 5. They could have another shape and for example frustoconical or flared towards the cavities 20, as shown in FIG. 6.
• the channels 30 'of FIG. 6 have an inlet section, that is to say a section taken at the orifice 32 by which the channel 30 opens out at the surface 22, less than their opposite exit section.
• Channels 30 have a section of substantially rectangular shape, circular or elliptical. This makes it possible in particular to limit the reduction of the attenuation frequency bandwidth induced by the length of the channels 30 ', that is to say by the height of the oil chamber 16.
• air passages 40 could be provided between the resonant cavities 20 to optimize heat exchange between them, at the expense of the acoustic performance. This option also makes it possible to overcome the problems related to the dilations of the partitions which define the cavities 20. These air passages may be located at the upper ends of the cavities (FIG. 7) or at their lower ends (FIG. 8).
• FIGS. 8 to 10 show other alternative arrangements, whose performance is slightly lower than those of parallel, parallel and independent fins.
• the fins are no longer independent but are instead linked together in pairs.
• the upper end of each fin 26 ' is connected by a material bridge 42 to the upper end of an adjacent fin 26'.
• the fins 26 "are rectilinear but not strictly parallel
• the fins 26" ' are generally wavy (non-rectilinear) and generally parallel in the second direction extension.
• the invention provides a solution to the real need to find a way to integrate the functions air / oil exchanger and acoustic treatment in the same equipment to no longer have competition between the two needs on an installation area.

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• Engineering & Computer Science (AREA)
• Chemical & Material Sciences (AREA)
• Combustion & Propulsion (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)
• Physics & Mathematics (AREA)
• Thermal Sciences (AREA)
• Structures Of Non-Positive Displacement Pumps (AREA)
• Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)
• Soundproofing, Sound Blocking, And Sound Damping (AREA)
• Turbine Rotor Nozzle Sealing (AREA)
• Supercharger (AREA)

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• 2014
  • 2014-10-29 FR FR1460375A patent/FR3028020B1/fr active Active
• 2015
  • 2015-10-23 US US15/517,085 patent/US11143462B2/en active Active
  • 2015-10-23 WO PCT/FR2015/052856 patent/WO2016066936A1/fr active Application Filing
  • 2015-10-23 RU RU2017111373A patent/RU2689264C2/ru active
  • 2015-10-23 CA CA2963496A patent/CA2963496C/fr active Active
  • 2015-10-23 EP EP15791715.4A patent/EP3213024B1/fr active Active
  • 2015-10-23 JP JP2017518303A patent/JP6723994B2/ja active Active
  • 2015-10-23 BR BR112017006895-8A patent/BR112017006895B1/pt active IP Right Grant
  • 2015-10-23 CN CN201580054172.XA patent/CN106795812B/zh active Active

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